WO2013123479A1 - Turbine à gaz et machine électrique - Google Patents

Turbine à gaz et machine électrique Download PDF

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Publication number
WO2013123479A1
WO2013123479A1 PCT/US2013/026588 US2013026588W WO2013123479A1 WO 2013123479 A1 WO2013123479 A1 WO 2013123479A1 US 2013026588 W US2013026588 W US 2013026588W WO 2013123479 A1 WO2013123479 A1 WO 2013123479A1
Authority
WO
WIPO (PCT)
Prior art keywords
gas turbine
turbine engine
component
electric machine
rotor
Prior art date
Application number
PCT/US2013/026588
Other languages
English (en)
Inventor
Mat French
William L. Siegel
Mark J. Blackwelder
Original Assignee
Rolls-Royce North American Technologies, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls-Royce North American Technologies, Inc. filed Critical Rolls-Royce North American Technologies, Inc.
Priority to EP13749687.3A priority Critical patent/EP2815485B1/fr
Priority to CA2864848A priority patent/CA2864848C/fr
Publication of WO2013123479A1 publication Critical patent/WO2013123479A1/fr
Priority to US14/461,721 priority patent/US9714609B2/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K21/00—Synchronous motors having permanent magnets; Synchronous generators having permanent magnets
    • H02K21/02—Details
    • H02K21/021—Means for mechanical adjustment of the excitation flux
    • H02K21/028—Means for mechanical adjustment of the excitation flux by modifying the magnetic circuit within the field or the armature, e.g. by using shunts, by adjusting the magnets position, by vectorial combination of field or armature sections
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
    • H02K7/1807—Rotary generators
    • H02K7/1823—Rotary generators structurally associated with turbines or similar engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • F02C7/266—Electric
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/76—Application in combination with an electrical generator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/304—Spool rotational speed
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K2213/00—Specific aspects, not otherwise provided for and not covered by codes H02K2201/00 - H02K2211/00
    • H02K2213/09—Machines characterised by the presence of elements which are subject to variation, e.g. adjustable bearings, reconfigurable windings, variable pitch ventilators
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K3/00—Details of windings
    • H02K3/04—Windings characterised by the conductor shape, form or construction, e.g. with bar conductors
    • H02K3/28—Layout of windings or of connections between windings

Definitions

  • the present invention generally relates to electric machines used with gas turbine engines, and more particularly, but not exclusively, to electric machines integrated with gas turbine engines.
  • One embodiment of the present invention is a unique gas turbine engine and electric machine.
  • Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for providing electric power from gas turbine engine operation. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
  • FIG. 1 is an embodiment of a gas turbine engine.
  • FIG. 2A is an embodiment of an electric machine integrated with a gas turbine engine.
  • FIG. 2B is an embodiment of an electric machine integrated with a gas turbine engine.
  • FIG. 3A is a configuration of windings of an electric machine.
  • FIG. 3B is a configuration of windings of an electric machine.
  • FIG. 3C is a configuration of windings of an electric machine.
  • FIG. 3D is a configuration of windings of an electric machine.
  • FIG. 4 depicts a chart of voltage change as a function of relative rotational speed.
  • FIG. 5A is an embodiment of an electric machine having a moveable member.
  • FIG. 5B is an embodiment of an electric machine having a moveable member.
  • a gas turbine engine 50 having turbomachinery components such as a compressor 52 and turbine 54, as well as a combustor 56.
  • the turbomachinery components can include one or more rotating rows of blades and additionally can include one or more rows of vanes, whether static or variable.
  • a shaft can be used in/with the gas turbine engine 50 and be configured to rotate at the same rate with one or more of the
  • turbomachinery components In the illustrated embodiment the shaft extends axially to connect the compressor 52 with the turbine 54, but other configurations are also contemplated herein.
  • the gas turbine engine 50 is depicted as a turbojet engine in the illustrated embodiment but can take on other forms such as a turboshaft, turboprop, and turbofan in other embodiments. As such, the gas turbine engine 50 can have any number of spools and take on any variety of forms. Additionally, the gas turbine engine can be configured as an adaptive cycle and/or variable cycle engine. In some forms the gas turbine engine can be used to provide power, such as propulsive power in one non-limiting
  • aircraft includes, but is not limited to, helicopters, airplanes, unmanned space vehicles, fixed wing vehicles, variable wing vehicles, rotary wing vehicles, unmanned combat aerial vehicles, tailless aircraft, hover crafts, and other airborne and/or extraterrestrial
  • present inventions are contemplated for utilization in other applications that may not be coupled with an aircraft such as, for example, industrial applications, power generation, pumping sets, naval propulsion, weapon systems, security systems, perimeter defense/security systems, and the like known to one of ordinary skill in the art.
  • FIGS. 2A and 2B one embodiment is depicted of an electric machine 58 coupled with the gas turbine engine 50 and having a rotor 60 that rotates at the same rate as a shaft of the gas turbine engine 50.
  • the electric machine 58 also includes a stator 62 which interacts with the rotor 60 during operation of the electric machine.
  • the electric machine 58 is capable of generating electricity by relative rotation of the rotor 60 and stator 62.
  • the embodiment of the electric machine 58 depicted in the illustrated embodiment is integrated with a fan 64 of the gas turbine engine 50, where the engine 50 is in the form of a turbofan. In other embodiments the electric machine 58 can be integrated to rotate with another shaft and/or another turbomachinery component.
  • the rotor 60 of the illustrated embodiment includes a magnetic field element 66 integrated with blades 68 of the turbomachinery component.
  • the magnetic field element 66 can take the form of a permanent magnet.
  • the magnetic field element 66 is disposed at the end of the blades 68 but can take different positions in other embodiments. Any number of magnetic field elements 66 can be used.
  • the stator 62 of the illustrated embodiment includes a number of coils 70 distributed around the annulus of the turbomachinery component.
  • Each of the coils can include any number of windings.
  • any number of coils having any variety of winding configurations can be used.
  • the coils 70 are depicted as protruding into a flow stream between a casing and the blades 68, it will be appreciated that in some embodiments the coils 70 are protected from the flow stream by a material covering.
  • a material covering can take a variety of forms, and in one non-limiting embodiment is material made from para- aramid synthetic fiber such as KEVLAR. Such a fiber could be woven together in a fabric or embedded in a matrix. Any variety of other material coverings are also contemplated herein.
  • C NBA (sin ⁇ )
  • N the number of windings on the coils
  • B the magnetic field
  • A is the area of coil perpendicular to the magnetic field
  • ⁇ is the relative rotational speed between the rotor 60 and stator 62.
  • some embodiments of the instant application are capable of adjusting voltage as a function of relative rotational speed by adjusting one or more of the other variables of the relationship, such as but not limited to the magnetic field and/or the number of windings on the coils.
  • FIGS. 3A-3D a series of diagrams depicting various configurations of the windings in a coil is illustrated.
  • the windings can be arranged in a variety of configurations during operation of the gas turbine engine. For example, during one mode of operation the windings can all be placed in series together as is depicted in FIG. 3A. In another mode of operation some of the windings can be placed in parallel with one other to create a parallel subset of windings, while the remaining windings are placed in series with each other and in series with the parallel subset of windings.
  • FIG. 3B depicts one
  • FIG. 3C depicts an additional winding placed in parallel with the windings that were placed in parallel in FIG. 3B, thus creating three windings in parallel, which are together placed in series with the remaining windings.
  • the voltage of this configuration is proportional to ( ⁇ -1) ⁇ ⁇ ⁇ ( ⁇ ).
  • FIG. 3D depicts all windings placed in parallel with each other. The voltage of this configuration is proportional to V CO N(CJ0N).
  • FIG. 4 depicts an embodiment where voltage provided from the electric machine 58 can be regulated as a function of relative rotational speed.
  • all windings can be configured in series relative to each other.
  • the windings can be placed in the configuration depicted in FIG. 3B which drops the voltage produced toward the x-axis depicted in the figure.
  • the voltage produced by the electric machine 58 also increases.
  • the windings can be placed in the configuration depicted in FIG. 3C which drops the voltage produced toward the x-axis depicted in the figure. This process can be repeated until all windings have been placed in parallel as shown in FIG. 3D.
  • the number of windings can be chosen to accommodate a wide range of relative rotational speeds of the rotor 60 and stator 62.
  • the configuration of the windings can be provided as described above in FIGS. 3A - 4 using any variety of manner of techniques.
  • the coils are placed in a given configuration using one or more mechanical switches as will be appreciated by those in the art.
  • FIGS. 5A and 5B one embodiment is depicted of a moveable member 72 capable of altering a magnetic field 74 utilized during operation of the electric machine 58.
  • the moveable member 72 can be a slip ring and in some forms can include a portion made of steel.
  • the moveable member 72 is shown coupled with the rotor 60 and is capable of being moved from the position depicted in FIG. 5A to the position depicted in FIG. 5B to reduce a magnetic field produced by the rotor 60.
  • Such a reduction can be provided as a function of relative rotational speed between the rotor 60 and the stator 62.
  • the moveable member 72 can occupy the position shown in FIG.
  • the fan blades 68 can be constructed such that a small angle would be present allowing for a conical shape, similar to that depicted in FIGS. 5A and 5B.
  • the moveable member 72 can be coupled with a device that provides a force to oppose motion of the moveable member 72.
  • a spring or other type of energy member can be used to resist movement of the moveable member 72.
  • the energy member can be used to withdraw the moveable member from the magnetic field to provide relatively large magnetic field to produce a voltage from the electric machine 58.
  • the force imparted to the moveable member 72 can be sufficiently large relative to the energy member such as to place the moveable member 72 in position shown in FIG. 5B to produce relatively low magnetic field. In this way the magnetic field is changed as a function of relative speed of the rotor 60 and stator 62.
  • the moveable member 72 can change position as a function of rotational speed such that voltage produced by the electric machine 58 when operated as a generator can be regulated to a desired level such as either a specific value or a desired range.
  • the moveable member 72 can be positioned in a location other than that depicted in FIGS. 5A and 5B to influence the magnetic field provided during operation of the electric machine 58.
  • the moveable member 72 can be located with or in proximity to the stator to change the magnetic field during rotation of the rotor.
  • the moveable member 72 can be in sliding arrangement with the coils and/or the material covering and as such would be static relative to the rotor 60.
  • the moveable member 72 could be moved between positions using any variety of devices such as an actuator.
  • any of the embodiments discussed above can stand alone or be combined with any one or more of the other embodiments.
  • a sensor can be used to detect one or more variables such as relative rotational speed between the rotor 60 and stator 62 to adjust a voltage provided by the electric machine 58 when operated as a generator.
  • Other sensors can additionally and/or alternatively be used to assess one or more conditions useful to adjust voltage.
  • a sensor that assesses position of the moveable member 72 can be used.
  • Information from the sensor can be incorporated with a controller in some embodiments useful to adjust voltage of the electric machine 58.
  • a controller can be comprised of digital circuitry, analog circuitry, or a hybrid combination of both of these types.
  • the controller can be programmable, an integrated state machine, or a hybrid combination thereof.
  • the controller can include one or more Arithmetic Logic Units (ALUs), Central Processing Units (CPUs), memories, limiters, conditioners, filters, format converters, or the like which are not shown to preserve clarity.
  • ALUs Arithmetic Logic Units
  • CPUs Central Processing Units
  • memories limiters, conditioners, filters, format converters, or the like which are not shown to preserve clarity.
  • the controller is of a programmable variety that executes algorithms and processes data in
  • operating logic that is defined by programming instructions (such as software or firmware).
  • operating logic for the controller can be at least partially defined by hardwired logic or other hardware.
  • the controller is configured to operate as a Full Authority Digital Engine Control (FADEC); however, in other embodiments it may be organized/configured in a different manner as would occur to those skilled in the art.
  • FADEC Full Authority Digital Engine Control
  • the present application provides an apparatus comprising a gas turbine engine having an electrical machine that includes a stator portion and rotor portion configured to interact and produce electrical power when rotated, the electrical machine integrated with a rotatable turbomachinery component of the gas turbine engine having a plurality of blades and a surface forming a flow path boundary radially outward of the plurality of blades, the rotor portion extending between blades of the rotatable turbomachinery component and located radially inward from the flow path boundary.
  • the gas turbine engine is a turbofan
  • the bladed rotor is a bladed fan component of the turbofan engine.
  • Another feature of the present application provides wherein the rotor portion located radially inward from the flow path boundary forms a bridge between blades of the rotatable turbomachinery component.
  • Still another feature of the present application provides wherein the bridge forms an annular construction around the entirety of the plurality of blades.
  • Yet still another feature of the present application provides wherein conductive coils of the electrical machine are located radially outward from the surface forming the flow path boundary such that the conductive coils are protected from a working fluid that flows through the turbomachinery component.
  • Still yet another feature of the present application further includes a voltage adjuster.
  • a further feature of the present application further includes a magnetic field adjuster.
  • Still another feature of the present application provides wherein the rotor is disposed at a radially outer end of the bladed turbomachinery component.
  • Yet still another feature of the present application provides wherein the rotor is radially inward of a surface forming a flow path of the gas turbine engine.
  • Still yet another feature of the present application provides wherein the gas turbine engine includes a fan and a bypass duct, and wherein the bladed turbomachinery component is the fan.
  • a further feature of the present application further includes magnetic field adjuster.
  • Still another aspect of the present application provides an apparatus comprising a gas turbine engine having a shaft drivingly connected to a row of blades structured to rotate within a passage and change a total pressure of a working fluid traversing the passage, the gas turbine engine also including an electric machine having a first component with coils and a second component having a moveable member capable of altering a magnetic field that interacts with the coils of the first component, the first and second components configured to rotate relative to one another at substantially the same rate as the shaft of the gas turbine engine, and wherein the moveable component is structured to alter the magnetic field as a function of rotational speed of the shaft.
  • a feature of the present application provides wherein the moveable component is urged from a first position to a second position via centripetal acceleration.
  • Another feature of the present application provides wherein the moveable component is slideable from the first position to the second position.
  • Still another feature of the present application further includes a biasing member that provides a force to the moveable component when it is in the second position.
  • the second component is a rotor of the electric machine, the rotor located radially inward of a flow path forming surface of the gas turbine engine.
  • a further feature of the present application provides wherein the second component includes a permanent magnet, and wherein the moveable component reduces the magnetic field created by the permanent magnet as a velocity of the shaft is increased.

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

L'invention concerne une machine électrique intégrée pour tourner avec un arbre d'une turbine à gaz. Dans un mode de réalisation, la machine électrique est intégrée avec un ventilateur de la turbine à gaz. Un rotor de la machine électrique peut être disposé à l'extrémité des pales de ventilateur et le stator intégré dans une surface formant un trajet d'écoulement de la turbine à gaz. Dans un mode de réalisation, les enroulements de la machine électrique peuvent changer de configuration, certains enroulements pouvant être placés parallèlement à un ou plusieurs autres enroulements, puis connectés ensemble en série avec les enroulements restants, s'il y a lieu. La tension de la machine électrique peut varier à la suite d'un changement de configuration des enroulements.
PCT/US2013/026588 2012-02-16 2013-02-18 Turbine à gaz et machine électrique WO2013123479A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13749687.3A EP2815485B1 (fr) 2012-02-16 2013-02-18 Turbine à gaz et machine électrique
CA2864848A CA2864848C (fr) 2012-02-16 2013-02-18 Turbine a gaz et machine electrique
US14/461,721 US9714609B2 (en) 2012-02-16 2014-08-18 Gas turbine engine and electric machine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201261599860P 2012-02-16 2012-02-16
US61/599,860 2012-02-16

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US14/461,721 Continuation US9714609B2 (en) 2012-02-16 2014-08-18 Gas turbine engine and electric machine

Publications (1)

Publication Number Publication Date
WO2013123479A1 true WO2013123479A1 (fr) 2013-08-22

Family

ID=48984807

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2013/026588 WO2013123479A1 (fr) 2012-02-16 2013-02-18 Turbine à gaz et machine électrique

Country Status (4)

Country Link
US (1) US9714609B2 (fr)
EP (1) EP2815485B1 (fr)
CA (1) CA2864848C (fr)
WO (1) WO2013123479A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2555100C1 (ru) * 2014-03-13 2015-07-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Роторная система магнитоэлектрической машины
EP3403932A1 (fr) * 2017-05-17 2018-11-21 General Electric Company Système de propulsion pour aéronef

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11014513B2 (en) 2016-05-18 2021-05-25 Rolls-Royce North American Technologies Inc. Control of low pressure generator for gas turbine engine
US11022042B2 (en) 2016-08-29 2021-06-01 Rolls-Royce North American Technologies Inc. Aircraft having a gas turbine generator with power assist
US10647438B2 (en) 2016-12-07 2020-05-12 Rolls-Royce North American Technologies, Inc. Variable pitch for coordinated control
ES2680793B1 (es) * 2017-01-24 2019-06-19 Ramos Angel Gabriel Ramos Motor eléctrico de bobina configurable
CN107313876B (zh) * 2017-07-04 2019-06-04 南京航空航天大学 一种用于航空涡扇发动机的磁悬浮外涵风扇
US11255215B2 (en) 2017-07-06 2022-02-22 Rolls-Royce North American Technologies Inc. Gas turbine engine with microchannel cooled electric device
FR3098846A1 (fr) * 2019-07-15 2021-01-22 Airbus Operations Groupe propulseur configuré pour déconnecter le rotor et le stator d’un moteur électrique
US11196320B2 (en) 2019-11-21 2021-12-07 Rolls-Royce Corporation Electric machine rotor
FI3945014T3 (fi) * 2020-07-30 2024-05-29 Ge Energy Power Conversion Technology Ltd Ulkoisen kuormituksen testauslaitteisto
US11606011B2 (en) 2020-08-10 2023-03-14 General Electric Company Electric machine
EP3968503A1 (fr) * 2020-08-31 2022-03-16 General Electric Company Turbomachine équipée d'une machine électrique intégrée dotée d'un stator segmenté et mobile
US11788428B2 (en) 2021-01-21 2023-10-17 Lockheed Martin Corporation Integrated hybrid propulsion system
US11661856B2 (en) 2021-03-19 2023-05-30 Rolls-Royce North American Technologies Inc. Gas turbine engine with embedded generator

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020117927A1 (en) 2001-02-28 2002-08-29 Kim Houng Joong Electric rotary machine and power generation systems using the same
US20080120980A1 (en) 2006-11-29 2008-05-29 Paul Robert Gemin Blade Tip Electric Machine
US20100014960A1 (en) * 2008-07-17 2010-01-21 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine engine with variable stator vanes
US20100127496A1 (en) * 2009-07-27 2010-05-27 Rolls-Royce Corporation Gas turbine engine with integrated electric starter/generator

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4367413A (en) 1980-06-02 1983-01-04 Ramon Nair Combined turbine and generator
US4720640A (en) 1985-09-23 1988-01-19 Turbostar, Inc. Fluid powered electrical generator
AU708514B2 (en) * 1995-10-13 1999-08-05 Nils Erik Gislason Horizontal axis wind turbine
GB2409936B (en) 2001-02-09 2005-09-14 Rolls Royce Plc Gas turbine with electrical machine
US6833631B2 (en) * 2001-04-05 2004-12-21 Van Breems Martinus Apparatus and methods for energy conversion in an ocean environment
GB0324785D0 (en) * 2003-10-24 2003-11-26 Electronica Products Ltd Magnetic gearing of permanent magnet brushless motors
DE102004004945A1 (de) 2004-01-31 2005-08-18 Mtu Aero Engines Gmbh Gasturbine, insbesondere Flugtriebwerk
DE102005046208A1 (de) * 2005-09-28 2007-03-29 Mtu Aero Engines Gmbh Strahltriebwerk
US7977842B2 (en) * 2006-10-05 2011-07-12 Lin Panchien Adaptive winding system and control method for electric machines
US20110000206A1 (en) * 2007-01-24 2011-01-06 Torok Aprad Progressive thermodynamic system
US8622688B2 (en) * 2007-03-23 2014-01-07 Flodesign Wind Turbine Corp. Fluid turbine
US8288982B2 (en) * 2010-12-10 2012-10-16 Current Motor Company, Inc. Permanent magnet motor with field weakening
US9024460B2 (en) * 2012-01-04 2015-05-05 General Electric Company Waste heat recovery system generator encapsulation

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020117927A1 (en) 2001-02-28 2002-08-29 Kim Houng Joong Electric rotary machine and power generation systems using the same
US20080120980A1 (en) 2006-11-29 2008-05-29 Paul Robert Gemin Blade Tip Electric Machine
US20100014960A1 (en) * 2008-07-17 2010-01-21 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine engine with variable stator vanes
US20100127496A1 (en) * 2009-07-27 2010-05-27 Rolls-Royce Corporation Gas turbine engine with integrated electric starter/generator

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2555100C1 (ru) * 2014-03-13 2015-07-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Роторная система магнитоэлектрической машины
EP3403932A1 (fr) * 2017-05-17 2018-11-21 General Electric Company Système de propulsion pour aéronef
US10807729B2 (en) 2017-05-17 2020-10-20 General Electric Company Propulsion system for an aircraft
EP4112475A1 (fr) * 2017-05-17 2023-01-04 General Electric Company Système de propulsion pour un aéronef

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Publication number Publication date
CA2864848C (fr) 2019-11-19
CA2864848A1 (fr) 2013-08-22
US20140356135A1 (en) 2014-12-04
EP2815485A1 (fr) 2014-12-24
EP2815485A4 (fr) 2017-06-07
EP2815485B1 (fr) 2021-04-07
US9714609B2 (en) 2017-07-25

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